Technical Report Archive & Image Library (TRAIL) - 28 Matching Results

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Analysis of Static Aeroelastic Behavior of Low-Aspect-Ratio Rectangular Wings

Description: "Slender-body theory is used in conjunction with late theory to analyze the static aeroelastic-divergence behavior of low-aspect-ratio rectangular wings of constant thickness when chordwise deformations are considered. In the analysis, the spanwise variation of the deflection is restricted to a parabola but the chordwise variation is allowed complete freedom. Results show the variation of the divergence speed and mode shape with the aspect ratio" (p. 1).
Date: April 1957
Creator: Hedgepeth, John M. & Waner, Paul G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bursting Strength of Unstiffened Pressure Cylinders with Slits

Description: Note presenting internal-pressure tests made on aluminum-alloy unstiffened cylinders with precut slits to study the effect of slit length and curvature on the hoop stress developed at the bursting pressure. The results are predicted with good accuracy by applying a curvature correction to the method presented in a previous report for computing the strength of flat plates with cracks.
Date: April 1957
Creator: Peters, Roger W. & Kuhn, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A collection of data for zero-lift damping in roll of wing-body combinations as determined with rocket-powered models equipped with roll-torque nozzles

Description: Report presenting the zero-lift damping-in-roll derivative as experimentally determined through high subsonic, transonic, and low supersonic speeds by a torque-nozzle forced-roll technique utilizing rocket-propelled models. Data from the the investigations is used to show the effects of wing plan form and airfoil section and the effects of aeroelasticity. Results regarding sweepback, aspect ratio, taper ratio, thickness ratio, airfoil-section shape, delta wings, increase in number of semispan w… more
Date: April 1957
Creator: Stone, David G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of an Interface on Transient Temperature Distribution in Composite Aircraft Joints

Description: Note presenting testing of geometrically related structural joints representing typical skin-stringer cross sections under radiant heating to simulate the effects of aerodynamic heating. The presence of an interface was found to have a significant effect on the temperature distribution in all geometries tested and thus must be considered in temperature calculations. Interface conductance values were computed for each of the 15 fabricated specimens.
Date: April 1957
Creator: Barzelay, Martin E. & Holloway, George F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of fuselage length and a canopy on the static longitudinal and lateral stability characteristics of 45 degrees sweptback airplane models having fuselages with square cross sections

Description: Report presenting a wind-tunnel investigation at low speed to determine the effects of fuselage nose length and a canopy on the static longitudinal and lateral stability characteristics of a complete model with a fuselage with square cross sections, a 45 degree sweptback wing, and a 45 degree sweptback horizontal tail.
Date: April 1957
Creator: Jaquet, Byron M. & Fletcher, H. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of spanwise variations in gust intensity on the lift due to atmospheric turbulence

Description: The effect of spanwise variations in gust intensity on the power spectrum directly due to atmospheric turbulence is calculated for several analytic approximations to the correlation function or power spectra of atmospheric turbulence, for several spanwise weighing functions (span loadings), and for various angles of sweepback.
Date: April 1957
Creator: Diederich, Franklin W. & Drischler, Joseph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Expected numbers of maxima and minima of a stationary random process with non-Gaussian frequency distribution

Description: Report presenting a method for calculating the expected number of maxima or minima of a random process with non-Gaussian frequency distribution from the statistical moments of the process and its first two derivatives. The effects of skewness and kurtosis can also be calculated provided the required moments are known.
Date: April 1957
Creator: Diederich, Franklin W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Experimental Hydrodynamic Investigation of the Inception of Vortex Ventilation

Description: Results are presented from a hydrodynamic investigation of the inception of vortex ventilation on modified-flat-plate rectangular lifting surfaces of aspect ratio 0.25 differing in scale and thickness ratio. Two types of bubble-formation processes are described. Inception speeds were correlated for bubble formation in the high angle-of-attack range by using the Froude number and for that in the low angle-of-attack range by expressing the speed as a function of the thickness ratio.
Date: April 1957
Creator: Ramsen, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimentally determined natural vibration modes of some cantilever-wing flutter models by using an acceleration method

Description: From Summary: "Three-dimensional views are presented of the first three natural vibration mode shapes of ten cantilever-wing models. A table of normalized deflections at six spanwise and five chordwise stations is included for each mode. These mode shapes were measured by a rather unique experimental technique using grains of sand as accelerometers."
Date: April 1957
Creator: Hanson, Perry W. & Tuovila, W. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exploratory study of ground proximity effects on thrust of annular and circular nozzles

Description: The proximity of the ground to an annular nozzle can result in thrust augmentation of up to 50 percent. The magnitude of thrust augmentation was a function of ground-to-nozzle distance, nozzle configuration, and nozzle pressure ratio. With a conventional circular nozzle a thrust reduction of 15 to 40 percent due to ground effect was obtained. The degree of thrust reduction was primarily a function of nozzle pressure ratio and ground-to-nozzle distance.
Date: April 1957
Creator: von Glahn, Uwe H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Full-Scale Investigation of Several Jet-Engine Noise-Reduction Nozzles

Description: A number of nozzles which use the mixing interference of adjacent jets for noise suppression were investigated. Reductions in sound power of nearly 70 percent (5 db) with thrust losses of 1 percent were achieved. A method of calculating the limiting frequency affected by this type of suppression nozzle, that is , multiple-slot nozzles, is presented. Data are shown which indicate that further large reductions in sound power are not likely with mixing-interference nozzles.
Date: April 1957
Creator: Coles, Willard D. & Callaghan, Edmund E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Further Experiments on the Stability of Laminar and Turbulent Hydrogen-Air Flames at Reduced Pressures

Description: "Stability limits for laminar and turbulent hydrogen-air burner flames were measured as a function of pressure, burner diameter, and composition. On the basis of a simple flame model, turbulent flashback involved a smaller effective penetration distance than laminar flashback. No current theoretical treatment predicts the observed pressure and diameter dependence of laminar and turbulent blowoff" (p. 1).
Date: April 1957
Creator: Fine, Burton
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ground Simulator Studies of the Effects of Valve Friction, Stick Friction, Flexibility, and Backlash on Power Control System Quality

Description: Note presenting tests on a power control system by means of a ground simulator to determine the effects of various combinations of valve friction and stick friction on the ability of the pilot to control the system. The results show that, when valve friction was present in a rigid system, the introduction of stick friction was beneficial in that it restored some of the quality lost because of the valve friction. Results regarding the rigid control system, flexible control system, and control sy… more
Date: April 1957
Creator: Brown, B. Porter
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic characteristics over a range of speeds up to 80 feet per second of a rectangular modified flat plate having an aspect ratio of 0.25 and operating at several depths of submersion

Description: Results of an investigation of the hydrodynamic characteristics over an extended speed range of a rectangular modified flat plate having an aspect ratio of 0.25 and operating at several depths of submersion are presented. Comparisons between these data and data over a lower speed range on a similar aspect-ratio-0.25 flat plate but having one-half the thickness are presented. These comparisons show no significant differences at the low speeds. At high speeds and high angles of attack, where exte… more
Date: April 1957
Creator: Vaughan, Victor L., Jr. & Ramsen, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrogen-oxygen explosions in exhaust ducting

Description: Results from an experiment indicated that the ignition of hydrogen-oxygen gas mixtures at a pressure of 1 atmosphere in a 2-foot-diameter duct resulted in detonation combustion. The use of a duct for the rocket exhaust may permit a reduction of the noise output and allow for the cooling and chemical treatment of the exhaust gases. The use of water jets and water sprays distributed through the duct did not prevent a detonation but did reduce peak pressure.
Date: April 1957
Creator: Ordin, Paul M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Incompressible Flutter Characteristics of Representative Aircraft Wings

Description: Note presenting the results of a detailed study of the flutter characteristics of four representative aircraft wings. During the investigation, eight important parameters of each wing were varied and the effects of mass, inertia, pitching spring, and location of a concentrated mass for all four wings and several sweepback angles.
Date: April 1957
Creator: Wilts, C. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a full-scale, cascade-type thrust reverser

Description: A double set of turning vanes was carried inside the jet tailpipe. To produce reverse thrust, the tailpipe opens into two side sections and the turning vanes move outward to form a V-shaped cascade, which deflects the exhaust-gas flow. Forward and reverse net thrust were measured over a range of engine speeds with the airplane stationary. Taxi tests were made to determine the comparative stopping distances using wheel braking and reverse thrust separately, and a combination of both. The effect … more
Date: April 1957
Creator: Kohl, Robert C. & Algranti, Joseph S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a nonlinear control system

Description: A discontinuous variation of coefficients of the differential equation describing the linear control system before nonlinear elements are added is studied in detail. The nonlinear feedback is applied to a second-order system. Simulation techniques are used to study performance of the nonlinear control system and to compare it with the linear system for a wide variety of inputs. A detailed quantitative study of the influence of relay delays and of a transport delay is presented.
Date: April 1957
Creator: Flügge-Lotz, I. & Taylor, C. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of semivaneless turbine stator designed to produce axially symmetrical free-vortex flow

Description: From Summary: "A semivaneless turbine stator designed to eliminate blade wakes and secondary-flow accumulations of boundary-layer air was built and tested. Performance of this stator was evaluated with static pressures measured in the vaneless section and surveys of total pressure and flow angle made at the stator exit. Results are presented in terms of theoretical and experimental velocities and flow angles, boundary-layer parameters, and contours of total-pressure loss across the stator."
Date: April 1957
Creator: Rohlik, Harold E. & Wintucky, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Limited Correlation of Atmospheric Sounding Data and Turbulence Experienced by Rocket-Powered Models

Description: Note presenting an analysis and comparison of atmospheric turbulence as experienced by rocket-powered models and temperature lapse-rate data obtained from rawinsonde soundings in 38 cases by using an assumed temperature lapse-rate stability boundary as a basis for comparison. A limited correlation has been obtained which indicates that atmospheric conditions classified as being unstable will generally be turbulent, but a marginal or stable classification does not necessarily indicate smooth air. more
Date: April 1957
Creator: Mason, Homer P. & Gardner, William N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The linearized subsonic flow about symmetrical nonlifting wing-body combinations

Description: Report presenting methods for determining the linearized subsonic flow about symmetrical, nonlifting wing-body combinations. A comparison of theory and experiment is made for two 45 degree sweptback wings in combination with basic Sears-Haack bodies of revolution and in combination with basic bodies indented according to the transonic area rule.
Date: April 1957
Creator: McDevitt, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of the Nonlinear Variation With Temperature of Heat-Transfer Rate From Hot Wires in Transonic and Supersonic Flow

Description: Note presenting equilibrium temperatures and heat-transfer rates for 0.00015- and 0.00030-inch diameter tungsten wires normal to the flow throughout a range of Mach numbers and Reynolds numbers. For the range of variables, equilibrium temperature of the hot wire is characterized by constant recovery factor for subsonic Mach numbers but constant equilibrium to total temperature ratio for supersonic Mach numbers. Results regarding the equilibrium temperature tests and heat-transfer tests are prov… more
Date: April 1957
Creator: Winovich, Warren & Stine, Howard A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A note on the effect of heat transfer on peak pressure rise associated with separation of turbulent boundary layer on a body of revolution (NACA RM-10) at a Mach number of 1.61

Description: Report presenting an investigation to determine the effect of heat transfer on the peak pressure rise associated with the separation of a turbulent boundary layer on a body of revolution at Mach number 1.61. The results indicated that little or no effect of heat transfer on the shock angles associated with separation on the peak pressure rise required to separate a turbulent boundary layer.
Date: April 1957
Creator: Czarnecki, K. R. & Sinclair, Archibald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The response of an airplane to random atmospheric disturbances

Description: The statistical approach to the gust-load problem which consists in considering flight through turbulent air to be a stationary random process is extended by including the effect of lateral variation of the instantaneous gust intensity on the aerodynamic forces. The forces obtained in this manner are used in dynamic analyses of rigid and flexible airplanes free to move vertically, in pitch, and in roll. The effect of the interaction of longitudinal, vertical, and lateral gusts on the wing stres… more
Date: April 1957
Creator: Diederich, Franklin W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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